Gas turbine engine components and cooling cavities

ABSTRACT

The present disclosure relates to gas turbine engine components including cooling cavities. One embodiment is directed to a component including a forward surface, an aft surface, at least one inlet on the forward surface and a cavity between the forward surface and the aft surface. The cavity is configured to receive airflow from at least one inlet to provide cooling flow for the component. The cavity includes a plurality of structures within the cavity. The component also includes at least one exit between the forward surface and the aft surface. The plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit. The component having a cavity may be employed by a combustor of a gas turbine engine.

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of U.S. Provisional PatentApplication No. 62/095,529 filed on Dec. 22, 2014, the entire contentsof which are incorporated herein by reference thereto.

FIELD

The present disclosure relates to components of a gas turbine engineand, in particular, a component having a cooling cavity.

BACKGROUND

Gas turbine engine combustors are required to operate efficiently duringengine operation and flight. Combustors are locations of tremendousamounts of heat. Combustors also experienced a high degree of heat anddistress. High heat exposure to the combustor may cause loss ofprotective thermal barrier coating which leads to exposure to a hot gasenvironment. This, in turn, leads to deformities of the combustor whichhave an adverse effect on cooling airflow and back side heat transfercoefficients. Film cooling alone may not remedy this situation and mayworsen the condition due to the addition of more air (and oxygen) whichcould increase combustion temperature.

Accordingly, it is desirable to provide components which minimize orlimit heat exposure causing deformities and maximizing cooling airflowwithin a gas turbine engine.

BRIEF SUMMARY OF THE EMBODIMENTS

Disclosed and claimed herein are components for a gas turbine engine.One embodiment is directed to a component including a cooling cavity.The component includes a forward surface, an aft surface, and at leastone inlet on the forward surface, the at least one inlet configured toreceive air flow. The component includes a cavity between the forwardsurface and the aft surface, wherein the cavity is configured to receiveairflow from the at least one inlet to provide cooling flow for thecomponent and wherein the cavity includes a plurality of structureswithin the cavity. The component includes at least one exit between theforward surface and the aft surface, the at least one exit configured toallow airflow to exit the cavity, wherein the plurality of structuresare configured to meter air flow within the cavity and to maintain thecooling effectiveness of air flow within the cavity from the at leastone inlet to the at least one exit.

In one embodiment, the forward surface is a cold side of a combustorbulkhead, and the aft surface is the hot side of the combustor bulkhead.

In one embodiment, the at least one inlet is configured to receiveairflow directed to a combustor of a gas turbine engine.

In one embodiment, the component is a structure including one or moreedges, and wherein the cavity is positioned proximate to an edge of thecomponent.

In one embodiment, the at least one exit is a cavity exit, and whereinthe at least one exit is positioned along the edge of the component anddisplaced from the at least one inlet.

In one embodiment, the plurality of structures are configured to meterair flow by directing airflow within the cavity based on one or more ofstructure spacing, structure size, structure shape, and structurepattern.

In one embodiment, the plurality of structures maintains coolingeffectiveness of airflow by allowing greater flow within a first portionof the cavity and reduced flow in a second portion of the cavity,wherein the second portion of the cavity is associated with the at leastone exit of the cavity.

In one embodiment, the plurality of structures are configured to providea cooling efficiency that increases as the airflow traverses the cavity,wherein cooling efficiency is a measure of heat pickup by airflow withinthe cavity.

In one embodiment, component is configured to interface with a secondcomponent, and a plurality of structures associated with the exit of thecomponent are offset from a plurality of structures associated with anexit of the second component.

In one embodiment, at least a first portion of the plurality ofstructures are configured to provide higher cooling efficiency and asecond portion of the plurality of structures are configured to providea higher cooling effectiveness.

Another embodiment is directed to a combustor of a gas turbine engine.The combustor includes a combustor shell, wherein the shell isconfigured to engage bulkhead and a bulkhead. The bulkhead includes aplurality of bulkhead panels. Each bulkhead panel includes a forwardsurface, an aft surface, and at least one inlet on the forward surface,the at least one inlet configured to receive air flow. Each bulkheadpanel includes a cavity between the forward surface and the aft surface,wherein the cavity is configured to receive airflow from the at leastone inlet to provide cooling flow for the component and wherein thecavity includes a plurality of structures within the cavity. Eachbulkhead panel includes at least one exit between the forward surfaceand the aft surface, the at least one exit configured to allow airflowto exit the cavity, wherein the plurality of structures are configuredto meter air flow within the cavity and to maintain the coolingeffectiveness of air flow within the cavity from the at least one inletto the at least one exit.

In one embodiment, the forward surface is a cold side of a bulkheadpanel, and the aft surface is the hot side of said bulkhead panel.

In one embodiment, the at least one inlet is configured to receiveairflow directed to a combustor of a gas turbine engine.

In one embodiment, the component is a structure including one or moreedges, and wherein the cavity is positioned proximate to an edge of thecomponent.

In one embodiment, the at least one exit is a cavity exit, and whereinthe at least one exit is positioned along the edge of the component anddisplaced from the at least one inlet.

In one embodiment, the plurality of structures are configured to meterair flow by directing airflow within the cavity based on one or more ofstructure spacing, structure size, structure shape, and structurepattern.

In one embodiment, the plurality of structures maintains coolingeffectiveness of airflow by allowing greater flow within a first portionof the cavity and reduced flow in a second portion of the cavity,wherein the second portion of the cavity is associated with the at leastone exit of the cavity.

In one embodiment, the plurality of structures are configured to providea cooling efficiency that increases as the airflow traverses the cavity,wherein cooling efficiency is a measure of heat pickup by airflow withinthe cavity.

In one embodiment, component is configured to interface with a secondcomponent, and a plurality of structures associated with the exit of thecomponent are offset from a plurality of structures associated with anexit of the second component.

In one embodiment, at least a first portion of the plurality ofstructures are configured to provide higher cooling efficiency and asecond portion of the plurality of structures are configured to providea higher cooling effectiveness.

In one embodiment, a gas turbine engine component including a coolingcavity is provided. The component having: a forward surface; an aftsurface; at least one inlet on the forward surface, the at least oneinlet configured to receive air flow; a cavity between the forwardsurface and the aft surface, wherein the cavity is configured to receiveairflow from the at least one inlet to provide cooling flow for thecomponent and wherein the cavity includes a plurality of structureswithin the cavity; and at least one exit between the forward surface andthe aft surface, the at least one exit configured to allow airflow toexit the cavity, wherein the plurality of structures are configured tometer air flow within the cavity and to maintain the coolingeffectiveness of air flow within the cavity from the at least one inletto the at least one exit.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the forward surface isa cold side of a combustor bulkhead, and the aft surface is the hot sideof the combustor bulkhead.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the at least one inletis configured to receive airflow directed to a combustor of a gasturbine engine.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the component is astructure including one or more edges, and wherein the cavity ispositioned proximate to an edge of the component.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the at least one exitis a cavity exit, and wherein the at least one exit is positioned alongthe edge of the component and displaced from the at least one inlet.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the plurality ofstructures are configured to meter air flow by directing airflow withinthe cavity based on one or more of structure spacing, structure size,structure shape, and structure pattern.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the plurality ofstructures maintains cooling effectiveness of airflow by allowinggreater flow within a first portion of the cavity and reduced flow in asecond portion of the cavity, wherein the second portion of the cavityis associated with the at least one exit of the cavity.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the plurality ofstructures are configured to provide a cooling efficiency that increasesas the airflow traverses the cavity, wherein cooling efficiency is ameasure of heat pickup by airflow within the cavity.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the component isconfigured to interface with a second component, and a plurality ofstructures associated with the exit of the component are offset from aplurality of structures associated with an exit of the second component.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, at least a firstportion of the plurality of structures is configured to provide highercooling efficiency and a second portion of the plurality of structuresare configured to provide a higher cooling effectiveness.

In yet another embodiment, a combustor of a gas turbine engine isprovided. The combustor having: a combustor shell, wherein the shell isconfigured to engage bulkhead; and a bulkhead including: a plurality ofbulkhead panels, wherein each bulkhead panel includes a forward surface;an aft surface; at least one inlet on the forward surface, the at leastone inlet configured to receive air flow; a cavity between the forwardsurface and the aft surface, wherein the cavity is configured to receiveairflow from the at least one inlet to provide cooling flow for thecomponent and wherein the cavity includes a plurality of structureswithin the cavity; and at least one exit between the forward surface andthe aft surface, the at least one exit configured to allow airflow toexit the cavity, wherein the plurality of structures are configured tometer air flow within the cavity and to maintain the coolingeffectiveness of air flow within the cavity from the at least one inletto the at least one exit.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the forward surface isa cold side of a bulkhead panel, and the aft surface is the hot side ofsaid bulkhead panel.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the at least one inletis configured to receive airflow directed to a combustor of a gasturbine engine.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the component is astructure including one or more edges, and wherein the cavity ispositioned proximate to an edge of the component.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the at least one exitis a cavity exit, and wherein the at least one exit is positioned alongthe edge of the component and displaced from the at least one inlet.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the plurality ofstructures are configured to meter air flow by directing airflow withinthe cavity based on one or more of structure spacing, structure size,structure shape, and structure pattern.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the plurality ofstructures maintains cooling effectiveness of airflow by allowinggreater flow within a first portion of the cavity and reduced flow in asecond portion of the cavity, wherein the second portion of the cavityis associated with the at least one exit of the cavity.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the plurality ofstructures are configured to provide a cooling efficiency that increasesas the airflow traverses the cavity, wherein cooling efficiency is ameasure of heat pickup by airflow within the cavity.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, the component isconfigured to interface with a second component, and a plurality ofstructures associated with the exit of the component are offset from aplurality of structures associated with an exit of the second component.

In addition to one or more of the features described above, or as analternative to any of the foregoing embodiments, at least a firstportion of the plurality of structures are configured to provide highercooling efficiency and a second portion of the plurality of structuresare configured to provide a higher cooling effectiveness.

Other aspects, features, and techniques will be apparent to one skilledin the relevant art in view of the following detailed description of theembodiments.

BRIEF DESCRIPTION OF THE DRAWINGS

The features, objects, and advantages of the present disclosure willbecome more apparent from the detailed description set forth below whentaken in conjunction with the drawings in which like referencecharacters identify correspondingly throughout and wherein:

FIG. 1 depicts a graphical representation of a gas turbine engineaccording to one or more embodiments;

FIGS. 2A-2C depict graphical representations of a component according toone or more embodiments;

FIGS. 2D-2E depict structures of a component according to one or moreembodiments; and

FIGS. 3A-3B depict graphical representations of a bulkhead according toone or more embodiments.

DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS Overview andTerminology

One aspect of this disclosure relates to components of a gas turbineengine, and in particular components with cooling cavities. One or morestructural configurations are provided for components to allow forcooling with a cavity or plenum of the component. The cavity positionand structures may allow for particular areas within a gas turbineengine or high temperature environment to receive cooling flow.According to another embodiment, configurations are provided to meterairflow and maintain cooling efficiency within a cavity of a component,such as a bulkhead.

According to another embodiment, configurations are provided forcomponents, such as combustors of gas turbine engines. By way ofexample, a combustor including a combustor shell may include one or morecavities in the bulkhead or bulkhead panels of the combustor. Althoughcomponents are described as bulkhead components, it should beappreciated that the principles may apply to other components.

A cavity as used herein related to an area or plenum within a structuralcomponent. In the context of a bulkhead, the cavity is in between theforward and aft surfaces of the bulkhead.

As used herein, the terms “a” or “an” shall mean one or more than one.The term “plurality” shall mean two or more than two. The term “another”is defined as a second or more. The terms “including” and/or “having”are open ended (e.g., comprising). The term “or” as used herein is to beinterpreted as inclusive or meaning any one or any combination.Therefore, “A, B or C” means “any of the following: A; B; C; A and B; Aand C; B and C; A, B and C”. An exception to this definition will occuronly when a combination of elements, functions, steps or acts are insome way inherently mutually exclusive.

Reference throughout this document to “one embodiment,” “certainembodiments,” “an embodiment,” or similar term means that a particularfeature, structure, or characteristic described in connection with theembodiment is included in at least one embodiment. Thus, the appearancesof such phrases in various places throughout this specification are notnecessarily all referring to the same embodiment. Furthermore, theparticular features, structures, or characteristics may be combined inany suitable manner on one or more embodiments without limitation.

Exemplary Embodiments

Referring now to the figures, FIG. 1 depicts a graphical representationof a gas turbine engine 100 according to one or more embodiments. Across-sectional representation is provided for components of gas turbineengine 100. Gas turbine engine 100 includes a combustor 105 which mayinclude one or more combustor shells, such as combustor shell 110.Components of a gas turbine engine, such as combustor 105 combustorshell 110, and gas turbine engine components in general, may beconfigured to include one or more features to allow for cooling.According to one embodiment, structural configurations are provided forcavities to allow for cooling, and in particular, providing componentswith a cavity including one or more structural elements within thecavity to meter air flow within the cavity. According to an exemplaryembodiment, and as described herein, a cooling cavity may be employed bycomponents of a hot section of gas turbine engine 100, such as combustor105. It should be appreciated though, that a cooling cavity, andcomponents including a cavity with structural elements as describedherein, may be employed with other types of components and non-gasturbine engine components in general.

Combustor 105 of FIG. 1 includes combustor shell 110. Combustor 105 mayinclude a plurality of combustion chambers or shells, such as combustorshell 110. Combustor shell 110 receives fuel injector 120 and providesan area for combustion of fuel and gases within the shell. Accordingly,portions of combustor shell 110 are exposed to high temperatures whichcan lead to distress. Film cooling may be applied to portions ofcombustor shell 110, however, portions of the combustor shell mayexperience more stress than others. By way of example, bulkhead 115 ofcombustor shell 110 may experience distress and possibly wear due toinadequate film cooling. Configurations including a cavity as describedherein may provide additional cooling to one or more regions of acomponent that experience higher levels of distress and wear.

Bulkhead 115 is depicted as a an annular component including an outercircumferential surface, such as outer rail 116, inner circumferentialsurface, such as inner rail 117 and opening 118. Bulkhead 115 may be thebulkhead for combustor shell 110.

Gas turbine engine 100 may include a plurality of combustors and/orcombustor shells 110. Gas turbine engine 100 may direct airflow, shownas airflow 125 towards combustor 105 and in particular combustor shell110. Output airflow of combustor shell 110 is shown as airflow 130.According to one embodiment, a component of a gas turbine engine, suchas bulkhead 115 may include one or more inlets to received airflow, suchas air flow 125. According to one embodiment, the inlets may be on aforward surface, shown as 135, of bulkhead 115. The component may havean aft surface, shown as 140. The component, such as bulkhead 115 mayinclude a cavity between forward surface 135 (cold side) and aft surface140 (hot side).

Referring now to FIGS. 2A-2E, FIGS. 2A-2C depict graphicalrepresentations of a component according to one or more embodiments.FIGS. 2D-2E depict structures of the component according to one or moreembodiments.

FIG. 2A depicts a representation of a component 200. According to oneembodiment, component 200 may be a component of a gas turbine engine(e.g., gas turbine engine 100), such as a bulkhead (e.g., bulkhead 115).As such, component 200 may relate to a section or panel of a bulkhead,such as a bulkhead panel or the bulkhead itself. In certain embodiments,component 200 may be part of an annular component, such as an annularbulkhead, and annular components in general.

Acceding to one embodiment, component 200 includes a cavity 205 whichmay be a cooling cavity for component 200. Component 200 includes one ormore inlets for cavity 205, such as inlets 210 configured to receiveairflow 215 (e.g., airflow 125). Cavity 205 provides a passageway forair flow 215 to cool the component, including the forward and aftsurfaces of the component, in the area associated with the cavity.Cavity 205 also allows airflow within the cavity to exit as shown by 216via one or more of exits 211. Cavity 205 may occupy a portion of thecomponent 205. Components may include multiple cavities per component.

Component 200 includes forward surface 220 which can include at leastone inlet 210. Component also includes an aft surface (represented as240). Air directed to and/or flowing toward forward surface 220, such asairflow directed to a combustor of a gas turbine engine, may be receivedby inlets 210. Component 200 includes at least one exit 211 between theforward surface 220 and the aft surface 240. The at least one exit 211may be configured to allow airflow within the cavity 205 to exit thecavity. According to one embodiment, exits 211 are offset or displacedfrom inlets 210. Exits 211 may be cavity exits and may be positionedalong the edge of component 200 and such that exits 211 are displacedfrom the at least one inlet 210.

The position of cavity 205 may be based on areas of component 200 thatneed additional cooling. In the context of a gas turbine enginecomponent and in particular a bulkhead, cavity 205 may be associatedwith positions of a bulkhead or bulkhead panel that need additionalcooling. Component 200 may be a structure including one or more edges,and cavity 205 may be positioned proximate to an edge of the component.Component 200 may optionally include opening 225 (e.g., opening 118)such as a fuel injector opening. In certain embodiments, cavity 205 maybe positioned relative to opening 225. By way of example, opening 225may be an opening for fuel injector, such that distress in the component200 due to combustion from the fuel injector may be modeled and/ordetermined. Cavity 205 may be associated with locations of distress forcomponent 200. According to another embodiment, cavity 205 may beposition between rails 230 (e.g., outer circumferential edge) and rail235 (e.g., inner circumferential edge) of the component 200.

Cavity 205 may be provided between the forward surface 220 and the aftsurface 240. Cavity 205 may be configured to receive airflow 215 fromthe at least one inlet 210 to provide cooling flow for the component 200and wherein the cavity 205 includes a plurality of structures within thecavity. As will be described in more detail below, component 200 mayinclude one or more structures internal to the cavity 205. In certainembodiments, cavity 205 may be formed by a refractory metal core, suchthat structures are formed within the cavity during a casting ormanufacturing process of component 200. Cavity 205 may be a plenum, suchas a plenum cooling space formed by a refractory metal core during acasting or formation process.

According to certain embodiments, component 200 may interface with oneor more similar components (e.g., panels). FIG. 2B depicts aconfiguration of component 200 with cavity 205 relative to component 201with cavity 206. Component 200 is configured to interface with a secondcomponent, component 201, and a plurality of structures associated withthe exit of the component 200 may be offset from a plurality ofstructures associated with an exit of the second component 201.Components 200 and 201 may be bulkhead panels, for example. According toone embodiment, components 200 and 201 may include cavities 205 and 206,respectively to provide cooling. Airflow exits of components 200 and 201are shown as 216 and 217, respectively. According to one embodiment,structures within cavities 205 and 206 may be arranged to allow forairflows 216 and 217 to efficiently exit. For example, structures withincavities 205 and 206 may be configured to stagger the exit points ofairflows 216 and 217.

FIG. 2C depicts structures of cavities 205 and 206 according to one ormore embodiments. Each cavity may include a plurality of structures.FIG. 2C depicts an exemplary representation (cut-away view) ofstructures for each of cavities 205 and 206.

Cavity 205 includes a plurality of structures, shown as structures 250and 255 configured to meter airflow within cavity 205. Cavity 205 mayreceive airflow form inlets 210. Airflow within cavity 205 is shown as245. Airflow 245 then exits cavity 205 and is shown as 216 relative toexits 211. Structures 250 and 255 of cavity 205 may be cylindricalpillars position in order to meter flow. Structures 250 are configuredto meter air flow by directing airflow within cavity 205 based on one ormore of structure spacing, structure size, structure shape, andstructure pattern. Structures 255 operate similar to structures 250.Structures 255 are at least one of a cylindrical and oblong shape.Structures 255 are positioned near an exit area of cavity 205. Accordingto one embodiment structures 255 may be shaped to control airflow 216that exits cavity 205.

Cavity 206 includes a plurality of structures, shown as structures 251and 256 configured to meter airflow within cavity 206. Structures 251and 256 of cavity 206 may operate similarly to structures of cavity 205.Cavity 206 may receive airflow from inlets 210 and airflow within cavity206 is shown as 246. Airflow 246 then exits cavity 206 and is shown as217 relative to exits of cavity 206. Structures 251 and 256 of cavity206 may be cylindrical pillars position in order to meter flow.According to another embodiment structures 255 of cavity 205 may bepositioned in an alternating location with structures 256 of cavity 206.

FIG. 2D depicts a representation of structures within a cavity accordingto one or more embodiments. Structures 250 may be configured to meterair flow within the cavity and to maintain the cooling effectiveness ofair flow within the cavity from the at least one inlet to the at leastone exit. Cooling flow 265 may be based on airflow received by inletsfor a cavity. One embodiment is directed to providing an arrangement ofstructures to maintain the ability of cooling flow 265 within a cavitysuch that air flow 267 exiting cavity may cool the component. Accordingto one embodiment, structures 250 may be arranged in sections.Structures 250 may also be arranged in rows or formations. FIG. 2Ddepicts an exemplary division 266 separating structures into firstportion 268 and second portion 269. By arranging structures to maintaincooling efficiency, cooling flow 270 near the exit of the cavity mayretain the ability to provide cooling effectiveness for the component.In that fashion, structures 250 are configured to meter airflow within acavity and to provide a cooling effectiveness that increases towards arail or exit of the cavity, such that cooling effectiveness is thecapacity to cool a portion of component.

FIG. 2E depicts a graphical representation of structures 250 within acavity of a component. According to one embodiment and regarding coolingprovided by structures, a portion of the structures may be associatedwith providing high efficiency cooling, and a portion of the structureswithin the cavity may be configured to provide high effectiveness.Structures 250 maintain cooling effectiveness of airflow by allowinggreater flow within a first portion of the cavity and reduced flow in asecond portion of the cavity, wherein the second portion of the cavityis associated with the at least one exit of the cavity. Structures mayalso be configured to provide a cooling efficiency that increases as theairflow traverses the cavity, wherein cooling efficiency is a measure ofheat pickup by airflow within the cavity. For example, a first portionof structures may be configured to provide higher cooling efficiency anda second portion of the plurality of structures may be configured toprovide a higher cooling effectiveness.

Structures 250 may be arranged such that a portion of the structures(e.g., rows 1-3) provide cooling with higher efficiency, shown as 280.According to another embodiment, Structures 250 may be arranged suchthat a portion of the structures (e.g., rows 4-6) provide cooling withhigher effectiveness, shown as 287. Structures 250 associated withsection 280 may be populated more densely, compared to the arrangementof structures in section 287 to provide effective and efficient heattransfer. In that fashion, the air flow may be controlled within acavity.

FIGS. 3A-3B depict graphical representations of a bulkhead according toone or more embodiments. According to one embodiment, bulkhead 300 mayinclude one or more cavities to provide cooling. FIG. 3A depicts aforward surface 301 of bulkhead 300. Bulkhead 300 may be an annularstructure. Bulkhead 300 may include a plurality of bulkhead panels 305_(1-n). Bulkhead 300 may be associated with the bulkhead of a combustorshell of a gas turbine engine (e.g., gas turbine engine 100). Bulkhead300 is represented as an annular bulkhead including a plurality ofcombustor panels 305 _(1-n). Bulkhead 300 and panels 305 _(1-n) may bearranged around a rotating axial shaft in opening 316 of gas turbineengine.

FIG. 3A depicts inlets 310 which may be configured to receive air flowfor a cavity within a panel of bulkhead 300. Inlets 310 are shown nearthe edge of bulkhead 300. The position of inlets 310 may be associatedwith the position of cavities within panels 305 _(1-n). The position ofinlets 310 may be exemplary. Inlets of bulkhead 300 may be positioned inother portions of panels 305. Exemplary inlet positions, which areoptional, for bulkhead 300 are shown as 311. Surface 301 may be aforward surface of the bulkhead 300. Bulkhead 300 is shown with openings320 for fuel injectors, with inner circumferential rail 315, panel rail325 between bulkhead panels, opening 316, and outer circumferential rail330.

FIG. 3B depicts an aft or back surface 302 of bulkhead 300. Bulkhead 300may include one or more cavities between forward surface 301 and aftsurface 302. Exemplary positions for cavities are shown as 335 and 340for bulkhead 300. These locations may be areas that may be susceptibleto distress and/or wear within a combustor shell. However, it should beappreciated that these areas are exemplary, and that cavities may beposition in other locations of bulkhead 300. Positions 335 relate topositions along an outer circumferential rail 330. Positions 340 relateto positions between panels and associated with panel rails 325. Whencavities are associated with positions between panels, such as panelrails 325, the structural elements of adjoining panels may be offsetwithin the cavities to allow for alternating exits paths of airflow.

While this disclosure has been particularly shown and described withreferences to exemplary embodiments thereof, it will be understood bythose skilled in the art that various changes in form and details may bemade therein without departing from the scope of the claimedembodiments.

What is claimed is:
 1. A gas turbine engine component including acooling cavity, the component comprising: a forward surface; an aftsurface; at least one inlet on the forward surface, the at least oneinlet configured to receive air flow; a cavity between the forwardsurface and the aft surface, wherein the cavity is configured to receiveairflow from the at least one inlet to provide cooling flow for thecomponent and wherein the cavity includes a plurality of structureswithin the cavity; and at least one exit between the forward surface andthe aft surface, the at least one exit configured to allow airflow toexit the cavity, wherein the plurality of structures are configured tometer air flow within the cavity and to maintain the coolingeffectiveness of air flow within the cavity from the at least one inletto the at least one exit.
 2. The component of claim 1, wherein theforward surface is a cold side of a combustor bulkhead, and the aftsurface is the hot side of the combustor bulkhead.
 3. The component ofclaim 1, wherein the at least one inlet is configured to receive airflowdirected to a combustor of a gas turbine engine.
 4. The component ofclaim 1, wherein the component is a structure including one or moreedges, and wherein the cavity is positioned proximate to an edge of thecomponent.
 5. The component of claim 4, wherein the at least one exit isa cavity exit, and wherein the at least one exit is positioned along theedge of the component and displaced from the at least one inlet.
 6. Thecomponent of claim 1, wherein the plurality of structures are configuredto meter air flow by directing airflow within the cavity based on one ormore of structure spacing, structure size, structure shape, andstructure pattern.
 7. The component of claim 1, wherein the plurality ofstructures maintains cooling effectiveness of airflow by allowinggreater flow within a first portion of the cavity and reduced flow in asecond portion of the cavity, wherein the second portion of the cavityis associated with the at least one exit of the cavity.
 8. The componentof claim 1, wherein the plurality of structures are configured toprovide a cooling efficiency that increases as the airflow traverses thecavity, wherein cooling efficiency is a measure of heat pickup byairflow within the cavity.
 9. The component of claim 1, whereincomponent is configured to interface with a second component, and aplurality of structures associated with the exit of the component areoffset from a plurality of structures associated with an exit of thesecond component.
 10. The component of claim 1, wherein at least a firstportion of the plurality of structures are configured to provide highercooling efficiency and a second portion of the plurality of structuresare configured to provide a higher cooling effectiveness.
 11. Acombustor of a gas turbine engine comprising: a combustor shell, whereinthe shell is configured to engage bulkhead; and a bulkhead including: aplurality of bulkhead panels, wherein each bulkhead panel includes aforward surface; an aft surface; at least one inlet on the forwardsurface, the at least one inlet configured to receive air flow; a cavitybetween the forward surface and the aft surface, wherein the cavity isconfigured to receive airflow from the at least one inlet to providecooling flow for the component and wherein the cavity includes aplurality of structures within the cavity; and at least one exit betweenthe forward surface and the aft surface, the at least one exitconfigured to allow airflow to exit the cavity, wherein the plurality ofstructures are configured to meter air flow within the cavity and tomaintain the cooling effectiveness of air flow within the cavity fromthe at least one inlet to the at least one exit.
 12. The combustor ofclaim 11, wherein the forward surface is a cold side of a bulkheadpanel, and the aft surface is the hot side of said bulkhead panel. 13.The combustor of claim 11, wherein the at least one inlet is configuredto receive airflow directed to a combustor of a gas turbine engine. 14.The combustor of claim 11, wherein the component is a structureincluding one or more edges, and wherein the cavity is positionedproximate to an edge of the component.
 15. The combustor of claim 14,wherein the at least one exit is a cavity exit, and wherein the at leastone exit is positioned along the edge of the component and displacedfrom the at least one inlet.
 16. The combustor of claim 11, wherein theplurality of structures are configured to meter air flow by directingairflow within the cavity based on one or more of structure spacing,structure size, structure shape, and structure pattern.
 17. Thecombustor of claim 11, wherein the plurality of structures maintainscooling effectiveness of airflow by allowing greater flow within a firstportion of the cavity and reduced flow in a second portion of thecavity, wherein the second portion of the cavity is associated with theat least one exit of the cavity.
 18. The combustor of claim 11, whereinthe plurality of structures are configured to provide a coolingefficiency that increases as the airflow traverses the cavity, whereincooling efficiency is a measure of heat pickup by airflow within thecavity.
 19. The combustor of claim 11, wherein component is configuredto interface with a second component, and a plurality of structuresassociated with the exit of the component are offset from a plurality ofstructures associated with an exit of the second component.
 20. Thecombustor of claim 11, wherein at least a first portion of the pluralityof structures are configured to provide higher cooling efficiency and asecond portion of the plurality of structures are configured to providea higher cooling effectiveness.